Aeroplane.



H. B. CHALMERS.

AEROPLANE.

APPLICATION FILED AUG.3. I910 1,145,9Y2; Patented July 13, 1915.

2 SHEETS-SHEET1.

WlTNESSES: INVENTOR ATTORNEY H. B. CHALMERS.

AEROPLANE.

wwucmou men AUG. 3. 1910.

1,145,972 PatvntedJuly 13, 1915.

Y 2 SHEETS-SHEET 2.

ATTORNEY HARRY B. oHALMEns, or DEDHAM,1VIASSACHUSETTS.

AEROPLANE.

Specification of Letters Patent.

Patented July 13, 1915.

mama fiieanu ust-s, i910. Serra-11%. 575,218.

America, have invented certain new .and useful Improvements in heropla'nes, of which the following is'a specification.

My invention relates to aeroplanes, and its object is to provide an apparatus of this kind ofsimple construction-andwith a simple system of control. a

I will describe my invention in the following specification and point out the novel features thereof in the appended claims.

. Referring to the drawings, Figure 1 is a side elevation of an aeroplane made according to my invention. Fig. 2 is a front elevation of the same apparatus, and in Fig. 3

I have shown it in plan view. Fig. 4 shows in sectional front elevation a detail of the control mechanism.

Like characters of reference designate corresponding parts in all of the figures.

' 10 designates a horizontal rectangular frame to the front corners of which are af- -.fi'xed a pair of risers 11 which are jointed together at their upper ends and to a stiif longitudinal spar 12. 13 designates another pair of risers which are aflixed to the rear corners of the .frame 10 and to the spar 12. A transverse spar 14 is also ailixed to the risers 11 at right-angles to the spar 12, and rigidly held thereon by braces 15. It may be further secured by means of wires 16 running It is to be understood that this structurejisshown diagrammatically, and that it maybe constructed with many cross-braces;,=wires.s and'other parts as may be foui clneces'sary to afford it the required strength.

- Supported on the frame 10 are one or two "motors 20 which are arranged to. drive a propeller shaft 21 on the forward end of which is the propeller 22. If preferred, the propellergmay be on the rear end of the shaft in the position indicated by dotted lines in Fig. 1 and designated by 22%;

30, 30 designate the planes, each of which is'builtup on a relatively stiff frame of desired shape, the front edge of which is affixed to the transverse spar 14, or is formed thereby. These planes or wings are rotatable about the spar 14 as an axis. They maybe loosely pivoted on this spar but are preferably connected thereto with sufiicient rigidity to aid in sustaining their own weight. Ifdesired a spar 18, lashed across [the uprights 13, may be provided to limit the downward movement of these wings.

The rear end of eachof these win'gs is connected by a'rod 31 with a tilting lever 32 which is rigidly affixed to the rear end of a shaft 33 supported in fixed hearings on the franie of the apparatus. of this shaft is provided with a yoke-like structure which forms bearings 34 for trunnions 35 projecting-from opposite sides of a tilting support 36' for the control shaft 37. 38 is a gear afiixed to this shaft at a point opposite the trunnions. These parts are shown-in Fig. 4.-

The rock shaft 32 may be tilted to one side or the other by means of this mechanism by merely pushing? the control shaft 37 to the left or to the right. This movement will then be transmitted to the two wings 3O tion as that shown at 30 in dotted lines in Fig. 1, and the other to be raised in a position such as that shown at 30 or to intermediate positions;

10. is a-rudder which comprises two rigid plane's 41 and 42 fastened-together at rightangles'to each other and connected to the rearendof thelongitudinal spar 12 by a universal-*1 oint' at 43. From points on oppo-' site: sidesofthe joint 43 on the forward,edge of...theplane- 42Jrun Wires 44. These wires are wound around a drum 45-011 the upper rend of a, vertical shaft"46. Near the lower 'endof this shaft is'fastened a gear 47- which is inmeshgwith the gear38 on the control shaft. By this mechanism the rudder may be turned-froni-sideito side by rotating the control shaft. Other Wires 48 run from the forward edge 'of-Fthe plahe 41' under -pulleys 49 on the frame-'10,.Ia'nd to the tilting sup port 36 to. which theyfare attached, the, one

The forward end from the upper edgeof the plane to a point thereon below the trunnions 35, and the one from the lower edge to a point above the ting the teeth of these gears out of mesh.

The manner of obtaining the control movements has been described, and the rest of the operation of the apparatus is obvious. By a single control shaft the operator may tilt the main planes or wings to obtain the proper balance of the machine; he may move the rudder up or down to steer the machine up or down, or he may move the rudder side- If desired a vertical stability plane of some such character as that disclosed in a copending application for Letters Patent, Serial Number 575,320, filed by me on the 3rd day of August, 1910, may be added to this apparatus by affixing it to the longi, tudinal spar 12.

What I claim is 1. Inan'aeroplane, a 'frame therefor comprising a transverse spar in the front thereof and a .lon itudinal spar running rearwardly there rom, a pair of supporting wings projecting rearwardly from the transverse spar at either side of the longitudinal spar, a control shaft, a supporting shaft upon which said control shaft is mounted,

and connections between said supporting shaft and the wings whereby the positions of said wings maybe simultaneously adj usted in opposite directions by moving the control shaft sidewise.

2. In an aeroplane, a frame therefor comprising a transverse spar in the front thereof and a longitudinal spar running rearwardly therefrom, a pair of supporting Wings projecting rearwardly from the transverse spar at either side of the longitudinal spar, a horizontal rudder mounted upon the rear end of the longitudinal spar, a control shaft, a supporting shaft upon which said control shaft is mounted, connections between said supporting shaft and the wings whereby the positions of said wings may be simultaneously adjusted in opposite directions by swinging said control shaft as a whole sidewise and other connections be-' tween the control shaft and the horizontal rudder whereby the rudder may be moved up and down by swinging the control .shaft forward and backward.

'3. In an aeroplane, a frame therefor comprising a transverse spar in the front thereof and a longitudinal spar running rearwardly. therefrom, a pair of supporting wings projecting rearwardly from the transverse spar at either side of the longitudinal spar, a rudder mounted upon the rear end of the longitudinal spar, a control shaft, a supporting shaft, a tilting member on the end thereof in which the control shaft is mounted, connections between said supporting shaft and the wings whereby the positions of said wings may be simultaneously adjusted in opposite directions by moving said control. shaft sidewise, and other connections between the tilting member and the rudder whereby the rudder may be tilted by moving the controlshaft back and forth.

4. In an aeroplane, a frame therefor comprising a transverse spar in the front thereof and a longitudinal spar running rearwardly therefrom, a pair of supporting wings projecting rearwardly from the transverse spar at either side of the longitudinal spar, a rudder having two planes at rightangles to each other pivotallyunounted upon the rear end of the longitudinal spar, a control shaft, a supporting shaft, a tilting member on the end thereof in which the control shaft is rotatably mounted, connections between said supporting shaft and the wings whereby the positions of said wings may be simultaneously adjusted in opposite directions by moving said contxol shaft sidewise, other connections comprising gearing between the control shaft and the rudder whereby the rudder may be moved sidewise by rotating the control shaft, and connections between the'tilting member and the rudder whereby the rudder may be tilted by moving the control shaft back and forth.

5. In an aeroplane, a fixed transverse spar, a pair of supporting wings projecting rearwardly from said spar on either side of the longitudinal aXis of the aeroplane, said wings being supported to rotate on said spar to assume positions of different inclination relative to the horizontal, a second 'transverse spar rearwardly arranged to limit the movement of saidwings, a substantially vertical controlling shaft supported to be dropped as a whole from side to side, and connections from said shaft to the wings whereby when said shaft is so rocked the Wings will be adjusted to positions of opposite inclination.

6. In an aeroplane, a frame therefor comprising a transverse spar and a longitudinal spar running rearwardly therefrom, a pair of supporting wings projecting rearwardly from said transverse spar on either side of the longitudinal spar, a rudder mounted upon the rear end of the longitudinal spar, a controlling shaft, a rock shaft upon which said controlling shaft is mounted to be rocked from side to side, rigid connections between said rock shaft and the wings whereby the positions of said wings may be simultaneously adjusted in opposite d1rec tions by lateral movement of said control- In testimony whereof I have signed my ling shaft, connections from the controlling name to this specification in the presence of shaft to the rudder operative to effect tilttwo subscribing Witnesses.

ing of the rudder upon longitudinal sWing- HARRY B. CHALMERS. 5 ing movement of said shaft, and connec- Witnesses:

tions actuated upon rotation of said control- ELLA LUoH,

ling shaft to move the rudder laterally. ERNEST W. MARSHALL.

Gopies of this patent may be obtained for five cents each, by addressing the Commissioner of Patents,

Washington, D. G. 

